Atr guide pins for sliding nacelle

ABSTRACT

A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon connecting portion and extending in the aft direction from the first annular portion. A second annular portion, aft of the first annular portion and coupled to the rail, is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage with the first annular portion when the second annular portion is in the closed position, thereby providing access to the engine core. A guide pin extends forward from the second annular portion. A locking mechanism is disposed within the first annular portion for engaging the guide pin when the second annular portion is in the closed position.

CROSS-REFERENCE TO RELATED APPLICATION(S)

This application claims priority to U.S. Provisional Application No.61/770,719, filed on Feb. 28, 2013, and entitled “ATR GUIDE PINS FORSLIDING NACELLE,” the disclosure of which is incorporated by referencein its entirety. This application also claims priority to U.S.Provisional Application No. 61/768,176, filed on Feb. 22, 2013, andentitled “ATR FULL RING SLIDING NACELLE,” the disclosure of which isincorporated by reference in its entirety. This application also claimspriority to U.S. Provisional Application No. 61/768,179, filed on Feb.22, 2013, and entitled “ATR SLIDING NACELLE WITH THRUST REVERSER,” thedisclosure of which is incorporated by reference in its entirety. Thisapplication also claims priority to U.S. Provisional Application No.61/768,184, filed on Feb. 22, 2013, and entitled “ATR INTEGRATED NOZZLEAND PLUG,” the disclosure of which is incorporated by reference in itsentirety. This application also claims priority to U.S. ProvisionalApplication No. 61/770,729, filed on Feb. 28, 2013, and entitled “ATRAXIAL V-GROOVE,” the disclosure of which is incorporated by reference inits entirety. This application also claims priority to U.S. ProvisionalApplication No. 61/770,735, filed on Feb. 28, 2013, and entitled “ATRPYLON FAIRING INTEGRATION,” the disclosure of which is incorporated byreference in its entirety.

BACKGROUND

Jet engines used in aerospace applications require periodic maintenanceand repair. Typically, such jet engines are gas turbine enginessurrounded by a nacelle. Part of the gas turbine engine surrounded bythe nacelle is a core that includes fan, compressor, combustor, andturbine sections. A bypass duct passes through the gas turbine engine,and fan blades pass through the bypass duct. The core generates powerthat is used to propel an attached aircraft. The core is used to drivefan blades in the bypass duct to generate thrust, and core exhaust alsocreates thrust to propel the aircraft.

In order to facilitate maintenance and repair of the engine, knownnacelles include doors that open outwards from the side of the nacelle,called “D-doors”. When the engine needs repair or maintenance, theD-door is opened to provide access to engine parts. Some of the enginecomponents that need regular maintenance or repair include the core andcore externals. D-doors typically provide access to components of thecore such as the combustor and turbine exhaust case that are notaccessible from either the upstream or downstream ends of the gasturbine engine. Core externals include those devices that support thefunctions of the core, such as oil supply and drain, fuel supply,sensors, and wiring and connections to the sensors.

Externals pass through the bypass duct of the gas turbine engine. Forexample, fuel lines, oil supply and drain lines, and sensor leads mustbe connected to fuel tanks, oil supply systems, and controllers that areoutside of the nacelle, respectively. Often, these externals are notsuitable for routing through the bypass duct unprotected. Externals areoften not structurally capable of supporting the loads that would beapplied on them in the bypass duct. Furthermore, externals are often notaerodynamic, and routing through the bypass duct would result inundesirable drag on the bypass airstream. For this reason, externals aretypically routed through a bifurcation, commonly referred to as a“bi-fi.” A bi-fi is typically shaped as an airfoil having low to zerocamber, and a chord direction parallel to the direction of the bypassairstream. The airfoil that makes up the bi-fi is hollowed out such thatexternals may be routed to the pylon or other sections of the aircraftwithout passing through the bypass airstream unprotected.

A common design of gas turbine engine has both an upper bi-fi and alower bi-fi. The upper bi-fi shelters externals passing between the coreand the pylon on which the engine is mounted. The lower bi-fi may beused for additional externals, or may be present to provide aerodynamicsymmetry to the bypass duct.

D-doors are often arranged at or near the mid-point, axially, of thenacelle in which they are housed. D-doors often open upwards in themanner typically described as a “butterfly door.” By opening theD-doors, a mechanic can gain access to the externals and/or core of theengine housed in the nacelle behind the D-door. Because the externalsare housed not only within the nacelle (i.e., behind the D-door) butalso within the bi-fi, known bi-fi designs are split such that they canalso open in the “butterfly door” manner, or removed entirely. In otherwords, known bi-fi constructions include two identical halves, each halfa mirror of the other side, which may be attached to one another to forma single airfoil surrounding the core externals of the gas turbineengine.

SUMMARY

A gas turbine engine nacelle includes a first annular portion that isstationary and adapted for partially surrounding an engine core. Thefirst annular portion includes a fore pylon connecting portion. A railis coupled to the fore pylon connecting portion and extending in the aftdirection from the first annular portion. A second annular portion, aftof the first annular portion and coupled to the rail, is movable alongan engine core centerline between a closed position and at least oneopen position. The second annular portion is configured to engage withthe first annular portion when the second annular portion is in theclosed position, thereby providing access to the engine core. A guidepin extends forward from the second annular portion. A locking mechanismis disposed within the first annular portion for engaging the guide pinwhen the second annular portion is in the closed position.

BRIEF DESCRIPTION OF THE DRAWINGS

FIGS. 1A-1C are side views of a gas turbine engine with a slidablenacelle aft portion in closed, partially open, and fully open positions,respectively.

FIG. 2 is a perspective view of the gas turbine engine of FIGS. 1A-1C,illustrating the rail and bi-fi systems.

FIG. 3A is a perspective view, in section, of mating portions of thefore nacelle and slidable portions.

FIGS. 3B-3C are enlarged side views of the locking mechanism shown inFIG. 3A, in partially open and closed positions, respectively.

FIG. 4A is a perspective view of a gas turbine engine in a closedconfiguration, the engine having a slidable nacelle aft portion thatincludes an aft pylon.

FIG. 4B is a perspective view of the gas turbine engine of FIG. 4A in anopen configuration.

FIG. 5A is a perspective view of a nozzle plug connected to a slidableportion and engaged with a turbine.

FIG. 5B is a perspective view of the nozzle plug, slidable portion, andturbine exhaust case of FIG. 5A, with the slidable portion and nozzleplug disengaged from the turbine.

DETAILED DESCRIPTION

A nacelle has a slidable aft portion that can be slid away from astationary fore portion along rails. The slidable aft portion allowsaccess to the core externals, and, when the gas turbine engine is in afully opened position, even allows for the core to be dropped out toundergo more extensive maintenance, repair, or replacement. The slidableportion can include a downstream portion of a bi-fi, so that coreexternals are accessible even when the slidable portion is in apartially-opened position. Various other improvements and configurationsare described herein that facilitate enhanced access to the engine.

FIGS. 1A-1C illustrate gas turbine engine 10 in three potentialpositions. FIG. 1A illustrates gas turbine engine 10 in a fully closedposition. This is the position gas turbine engine 10 would be in duringoperation. FIG. 1B illustrates gas turbine engine 10 in a partially openposition. The partially open position may be sufficient for somerepairs, modifications, or maintenance. FIG. 1C illustrates gas turbineengine 10 in a fully open position that may be helpful to carry outmajor repairs.

FIG. 1A is a side view of gas turbine engine 10. In FIG. 1A, the engineis in a fully closed or operational condition. Gas turbine engine 10 ismade up of three primary components: stationary portion 12, slidableportion 14, and rail 16.

Stationary portion 12 includes fore nacelle 18, fore pylon 20, andengine core 24 (shown in FIGS. 1B and 1C). Fore nacelle 18 enclosesvarious structures such as a fan, compressor sections, and/or bleed airsystems that are well known in the art. In the embodiment shown in FIG.1A, fore nacelle 18 is arranged about centerline C_(L). Stationaryportion 12 is attached to an aircraft (not shown) at fore pylon 20. Forepylon 20 is a part of a larger pylon system that may include bothstationary and movable components.

Slidable portion 14 is also centered about centerline C_(L). Slidableportion 14 is mounted on rail 16, which extends parallel to centerlineC_(L). Rail 16 is stationary, in that it is fixed relative to stationaryportion 12. Rail 16 may include a single track or multiple-track system.Slidable portion 14 is mounted to rail 16 such that slidable portion 14may be moved fore and aft along rails 16. In some embodiments, rail 16may be housed within part of a pylon system (not shown).

FIG. 1B is a side view of the gas turbine engine 10 shown in FIG. 1A. Asshown in FIG. 1B, gas turbine engine 10 is in a partially opencondition. Gas turbine engine 10 can be arranged in such partially opencondition, starting from the closed position shown in FIG. 1A, bysliding slidable portion 14 along rail 16 in the aft direction. Gasturbine engine 10 includes the components previously described withrespect to FIG. 1A. In addition, the view shown in FIG. 1B illustratesupper fore bi-fi 22U, lower fore bi-fi 22L, core 24, and externals 26.

Upper fore bi-fi 22U and lower fore bi-f 22L are fore portions of twobifurcations (commonly referred to as “bi-fi”s) that extend outward fromcore 24 to house externals 26. Upper fore bi-fi 22U and lower fore bi-fi22L extend radially outward from centerline C_(L) through a bypass duct(not shown). Upper fore bi-fi 22U and lower fore bi-fi 22L each form theleading edge of a larger bi-fi structure, described in more detail withrespect to FIG. 2.

Core 24 is a portion of gas turbine engine 10 that is arranged alongcenterline C_(L). Core 24, which typically includes combustor andturbine sections, generates power and thrust. Combustion of fuel andcompressed air in core 24 can be used to do work on a core airstream(not shown), which can in turn be used to generate thrust or drive othercomponents of gas turbine engine 10.

Externals 26 are used to support the functions of core 24. For example,externals include (but are not limited to) oil supply, oil sump, fuelsupply, and sensors. Externals 26 are arranged such that they arecircumferentially aligned with upper fore bi-fi 22U or lower fore bi-fi22L. In this way, when gas turbine engine 10 is in a closed position, asdescribed previously with respect to FIG. 1A, externals 26 are housedwithin a bi-fi structure as described with respect to FIG. 2 andprotected from bypass airflow during engine operation.

As can be seen in FIG. 1B, moving slidable portion 14 in the aftdirection results in access to core 24 and externals 26. Thus, slidableportion 14 includes all portions of gas turbine engine 10 that areradially outwards from core 24 behind a certain point in the aftdirection and under rail 16. Upon translation of slidable portion 14along rail 16 in the aft direction, no duct, liner, or housing remainsin place to inhibit access by a mechanic or inspector.

A mechanic may desire to put gas turbine engine 10 into thepartially-open position shown in FIG. 1B in order to service the engine.Often, for light maintenance or minor repairs, it is not necessary toremove (or “drop”) the core. Instead, a mechanic may be able todiagnose, maintain, or make light repairs by gaining access to core 24or externals 26, even though they are still mounted to an aircraft (notshown). By sliding slidable portion 14 along rail 16, some portions ofcore 24 and externals 26 are easily accessible. Furthermore, theconfiguration shown in FIG. 1B provides access from a wide variety ofangles to core 24 and externals 26, free from obstructions andinterference associated with hinged doors or access panels.

FIG. 1C shows gas turbine engine 10 of FIGS. 1A-1B in a “fully open”position. FIG. 1C illustrates the same components previously describedwith respect to FIG. 1B. In the engine configuration shown in FIG. 1C,slidable portion 14 has been moved so far aft that it is possible toaccess core 24 and externals 26 along their entire axial length. Infact, in the configuration shown in FIG. 1C, it is possible to drop core24 out of engine 10. Dropping core 24 is often beneficial forsignificant maintenance or engine overhauls. In the configuration shownin FIG. 1C, it is possible to drop core 24 without having to deconstructany blades, vanes, or other structures present in either stationaryportion 12 or slidable portion 14.

In alternative embodiments, fore nacelle 18 need not be centered aboutcenterline C_(L). Various other externals 26 may be present or missingfrom alternative embodiments. Rail 16 may not extend linearly in the aftdirection, but may be configured such that slidable portion 14 can bemoved along core 24 in any direction to enhance access to core 24 and/orexternals 26.

FIG. 2 is a perspective view of gas turbine engine 10, as previouslydescribed with respect to FIGS. 1A-1C. FIG. 2 shows gas turbine engine10 with the slidable portion 14 moved aft from the closed position. FIG.2 illustrates upper aft bi-fi 28U and lower aft bi-fi 28L, which areboth a part of slidable portion 14. Further, FIG. 2 illustrates InnerFixed Portion (“IFS”) 30 and aft nacelle 32. IFS 30 is an annularstructure that separates core 24 from bypass duct 34, which is definedby IFS 30 and aft nacelle 32.

Rail 16 shown in FIG. 2 is a two-track system that is affixed to forepylon 20. Slidable portion 14 is attached to rail 16 such that slidableportion 14 is movable along rail 16 along centerline C_(L) in the aftdirection.

Upper aft bi-fi 28U is configured such that, when gas turbine engine 10is in the closed position previously described with respect to FIG. 1A,upper aft bi-fi 28U engages with upper fore bi-fi 22U to surround atleast a portion of externals 26. Likewise, in the closed position loweraft bi-fi 28L engages with lower fore bi-fi 22L to surround at least aportion of externals 26. The structures formed by each pair of engagedbi-fis forms an airfoil that passes radially through bypass duct 34.Externals 26 are housed within the combined bi-fi structures to protectthe externals and reduce aerodynamic drag that would be caused byexposed externals 26 within bypass duct 34.

Although rail 16 is shown as a two-track system in FIG. 2, various otherconfigurations of rail 16 are possible. For example, in alternativeembodiments, rail 16 may be a single track.

FIG. 3A is a perspective view, in section, of mating portions of forenacelle 18 and slidable portion 14 in fully open position. Gas turbineengine 10, in addition to the components described in FIGS. 1A, 1B, 1C,and 2, includes axial groove 54, rib 58, guide pin 64 and lockingmechanism 74. Fore nacelle 18 includes first inner radial surface 52,axial groove 54, and locking mechanism 74. Slidable portion 14 includessecond inner radial surface 56, rib 38, and guide pin 64. Axial groove54 includes side walls 60 and base wall 62. Axial groove 54 and rib 58are configured to engage with each other when gas turbine engine 10 isin a closed position. Guide pin 64 includes pin shaft 66, and spearhead68. Spearhead 68 includes front segment 70 and back segment 72.

Similar to the corresponding components of gas turbine engine 10, asdescribed previously with respect to FIGS. 1A, 1B, 1C, and 2, slidableportion 14 can be in one of three positions, those being a fully closed,partially open, or fully open position. When partially or fully open, asdepicted in FIG. 3A, first inner radial surface 52 on fore nacelle 18 isspaced apart from second inner radial surface 56 on slidable portion 14.

First inner radial surface 52 is an aft facing surface, and includesaxial groove 54 and locking mechanism 74. Axial groove 54 extendsaxially inward (forward) from first inner radial surface 52 into forenacelle 18. Axial groove 54 forms a continuous circle about the diameterof first inner radial surface 52. In alternative embodiments, axialgroove 54 can form a discontinuous or fragmented circle about thediameter of first inner radial surface 52. Second inner radial surface56 is a forward facing surface that, in the closed position, engageswith first inner radial surface 52.

Locking mechanism 74 is disposed within first inner radial surface 52,spaced apart from guide pin 64 on second inner radial surface 56 in thepartially open and fully open positions. Locking mechanism 74 extendsinto fore nacelle 18. Locking mechanism is configured to receive andengage guide pin 64.

Second inner radial surface 56 is configured to engage axial groove 54.Specifically, rib 58 is the portion of second inner radial surface 56that engages axial groove 54. Rib 58 extends axially outward (forward)from second inner radial surface 56 and is spaced apart from axialgroove 54 on first inner radial surface 52 in the partially open andfully open positions. Rib 58 can be machined along with slidable portion14. Alternatively, rib 58 can be machined separately and mechanicallyfastened to slidable portion 14. The dimensions of rib 58 can beconfigured to substantially conform to and mate with the dimensions ofaxial groove 54. Rib 58 forms a continuous circle, commensurate withaxial groove 54 about the diameter of second inner radial surface 56. Inalternative embodiments, rib 58 can form a discontinuous circle aboutthe diameter of second inner radial surface 56.

Second inner radial surface 56 also includes guide pin 64. Guide pin 64extends axially outward (forward) from second inner radial surface 56.Guide pin 64 includes pin shaft 66 and spearhead 68. Pin shaft 66 iscylindrically shaped and can take on other shapes in differentembodiments. Spearhead 68 includes front segment 70 and back segment 72.Front segment 70 is conically shaped, but can take on other shapes indifferent embodiments, and is tapered to point toward first inner radialsurface 52. Back segment 72 is also conically shaped, and can take ondifferent shapes in alternative embodiments, and is tapered to pointtoward second inner radial surface 56.

In operation, as described with respect to FIGS. 1A, 1B, 1C and 2 above,gas turbine engine 10 can be in fully or partially open position toexpose engine core 24 or in a closed position during normal operationmode, (e.g., during flight). Gas turbine engine 10 moves from an openposition to a closed position as described previously with respect toFIGS. 1A, 1B, 1C, and 2. As slidable portion 14 slides towards forenacelle 18, rib 58 engages axial groove 54. Side walls 60, being nearlyv-shaped, can help to guide rib 58 into axial groove 54. Base wall 62provides a platform for rib 58 to engage axial groove 54. This can helpimprove the stability of the engagement between axial groove 54 and rib58. Rib 58 and axial groove 54 form a radial engagement. That is, duringnormal operation mode (e.g., during flight), rib 58 and axial grove 54are radially biased against each other. Rib 58 is configured tosubstantially conform to the dimensions of axial groove 54 thusproviding a secure radial engagement between fore nacelle 18 andslidable portion 14. When axial groove 54 and rib 58 are fully engaged,first inner radial surface 52 and second inner radial surface 56 are infull contact with each other. In other embodiments of gas turbine engine10 first inner radial surface 52 and second inner radial surface 56 maynot be in full contact with one another when the engine is in the closedposition around the full circumference of the engine. Although FIG. 3Ashows, and the previous text describes, axial groove 54 as located onfore nacelle 18, one having ordinary skill in the art will appreciatethat axial groove 54 could also be located on slidable portion 14 andrib 58 arranged on fore nacelle 18 without departing from the scope ofthe invention.

There are several advantages to using axial groove 54 and rib 58 tosecure fore nacelle 18 and slidable portion 14 of gas turbine engine 10including the following non-limiting examples. Because fore nacelle 18and slidable portion 14 are radially engaged in the closed position, thetwo portions are less likely to be radially displaced during normaloperation modes, (e.g., during flight). The engagement of axial groove54 and rib 58 can also create a seal between fore nacelle 18 andslidable portion 14. The seal is advantageous because it can help toprevent bypass airflow from being lost at the intersection of the twoportions, thus increasing the overall efficiency of gas turbine engine10. Similarly, the seal can also prevent outside air from entering gasturbine engine 10 at the intersection of the two portions. A furtheradvantage of the system is that axial groove 54 and rib 58 can help toposition fore nacelle 18 and slidable portion 14 such that the outersurfaces of each portion are flush with each other. This can provide gasturbine engine 10 with a smooth and virtually continuous surface when infully closed position. Accordingly, unnecessary drag and stress on gasturbine engine 10 can be reduced during flight.

Guide pin 64 engages locking mechanism 74 as rib 58 engages axial groove54. Locking mechanism 74 can receive front segment 70 and back segment72. Locking mechanism 74 then engages back segment 72 which places aback load on guide pin 64 and can help ensure proper engagement betweenfore nacelle 18 and slidable portion 14. Although locking mechanism 74and guide pin 64 are shown as disposed on first inner radial surface 52and second inner radial surface 56 respectively, one having ordinaryskill in the art will recognize that locking mechanism 74 and guide pin64 could be disposed on second inner radial surface 56 and first innerradial surface 52 respectively, without departing from the scope of thisinvention. Further, although fore nacelle 18 and slidable portion 14 aredepicted as having a single locking mechanism 74 and a single guide pin64, one having ordinary skill in the art will recognize that a pluralityof locking mechanisms 74 and guide pins 64 can be included withoutdeparting from the scope of the invention.

FIG. 3B is an enlarged side view of locking mechanism 74 and guide pin64 as described above with respect to FIG. 3A. Locking mechanism 74includes cavity 76 and collars 78. In FIG. 3B, gas turbine engine 10 isin a partially open position. Thus, guide pin 64 is axially spaced fromcavity 76. Locking mechanism 74 is configured to be disposed withinfirst inner radial surface 52 and receive guide pin 64 when gas turbineengine 10 is in the closed position. Prior to engaging guide pin 64,collars 78 are recessed within locking mechanism 74 which leaves cavity76 open.

FIG. 3C shows the locking mechanism 74 of FIG. 3B with gas turbineengine 10 in the closed position. Slidable portion 14 (FIGS. 1A-1C, 2)is brought into mating engagement with fore nacelle 18, and spearhead 68engages locking mechanism 74. As a result of its conical shape, frontsegment 70 is guided into cavity 76. When spearhead 68 is fullyencompassed within cavity 76, collars 78 are deployed to engage backsegment 72. Collars 78 are configured to engage back segment 72 bysubstantially matching the profile of back segment 72. In this way,collars 78 prevent axial displacement of guide pin 64. Collars 78 can bedeployed using a suitable actuator (not shown).

There are several advantages to using guide pin 64 and locking mechanism74 to secure fore nacelle 18 and slidable portion 14 including thefollowing non limiting examples. When back segment 72 is engaged bycollars 78 a back load is placed on guide pin 64 to ensure properengagement of fore nacelle 18 and slidable portion 14 which can helpreduce the risk of the two portions separating during flight.Additionally, guide pin 64 and locking mechanism 74 can help tofacilitate proper alignment of axial groove 54 and rib 58 as well assecure the connection between them. A further advantage is that guidepin 64 and locking mechanism 74 can help to position fore nacelle 18 andslidable portion 14 such that the outer surfaces of each portion areflush with each other. This can provide gas turbine engine 10 with asmooth and virtually continuous surface when in fully closed position.Accordingly, unnecessary drag and stress on gas turbine engine 10 can bereduced during flight.

FIGS. 4A-4B show gas turbine engine 110, which includes stationaryportion 112, slidable portion 114, and rail 116. FIG. 4A shows gasturbine engine 110 in the closed position. Gas turbine engine 110 issimilar to gas turbine engine 10 of FIGS. 1A-1C and 2. However, gasturbine engine 110 also includes aft pylon 136, which was not present ingas turbine engine 10. Aft pylon 136 is slidable to provide access toadditional components within gas turbine engine 110.

The components that make up gas turbine engine 110 are substantiallysimilar to the components previously described with respect to gasturbine engine 10 of FIGS. 1A-1C and FIG. 2. Stationary portion 112includes fore nacelle 118, fore pylon 120, upper fore bi-fi 122U, lowerfore bi-fi (not shown in this perspective), core 124, and externals 126.Slidable portion 114 includes upper aft bi-fi 128U, lower aft bi-fi128L, IFS 130, and aft nacelle 132. IFS 130 and aft nacelle 132 definebypass duct 134.

In addition to those components already described in detail previously,gas turbine engine 110 includes aft pylon 136. Aft pylon 136 is a partof slidable portion 114—that is, aft pylon travels along rail 116 whengas turbine engine 110 is rearranged between open, partially open, andclosed positions. In the embodiment shown in FIG. 4A, aft pylon 136 isconnected to aft nacelle 132, such that translation of aft nacelle 132along rail 116 causes an equal movement of aft pylon 136. Becauseslidable portion 114 is fully forward (that is, gas turbine engine 110is in a closed configuration), aft pylon 136 engages with fore pylon120. When engaged, fore pylon 120 and aft pylon 136 cooperate to housevarious structures such as supply lines, cables, and/or structuralsupports from any surrounding airstream. Fore pylon 120 and aft pylon136 may simply have complementary shapes to fit together, or may befastened to one another with a variety of known fastening mechanisms(not shown).

Aft pylon 136 cooperates with fore pylon 120 to house various componentsthat pass between gas turbine engine 110 and a related aircraft (notshown). Such components may include structural supports to affix gasturbine engine 110 to an aircraft wing, or fuel, oil, and/or electronicsconduits or passages between gas turbine engine 110 and various remotesystems, none of which are shown in FIG. 4A. In the event that thesevarious components need maintenance, replacement, or attention of anyother variety from a mechanic, placing gas turbine engine 110 in apartially open or open state facilitates access to those components.

Furthermore, aft pylon 136 increases the structural integrity ofslidable portion 114. Aft pylon 136 binds together those portions of aftnacelle 132 that are attached to rail 116. This reduces the potentialfor aft nacelle 132 to exert stresses on rail 116, and preventsdistension of aft nacelle 132.

FIG. 4B shows gas turbine engine 110 of FIG. 4A in an open position. Aspreviously described with respect to FIG. 4A, aft pylon 136 is slidableto provide access to additional components within gas turbine engine110. As shown in FIG. 4B, gas turbine engine 110 is at least partiallyopen, such that aft pylon 136 is separated from fore pylon 120. Thus, amechanic is able to inspect, repair, or replace components that weresurrounded by the engaged structure shown with respect to FIG. 4A.

In alternative embodiments, aft pylon 136 may be configured to movealong rail 116 independently of aft nacelle 132. In further alternativeembodiments, aft pylon 136 need not be configured to travel along rail116 at all, but may instead be detachable from fore pylon 120 when aftnacelle 132 is not in the closed position.

FIGS. 5A-5B illustrate the aftmost portion of gas turbine engine 210. Inparticular, FIGS. 5A-5B show a nozzle plug that is configured tocomplement the slidable portions of gas turbine engines previouslydescribed with respect to FIGS. 1A-1C, 2, and 4A-4B. Nozzle plugs areused in gas turbine engines to route exhaust gases through the turbineexhaust case. Nozzle plug geometry can affect aerodynamic performanceand engine acoustics. It is desirable to have the nozzle plug be movablewith the slidable portion, so that a wide variety of nozzle pluggeometries can be used without risking interference between the slidableportion and the nozzle plug that may have occurred if the nozzle plugremained affixed to the engine core.

FIG. 5A is a perspective view of gas turbine engine 210 in the closedposition. Gas turbine engine 210 includes many similar components to gasturbine 10 and gas turbine engine 110 previously described. Inparticular, gas turbine engine 210 includes core 224, aft nacelle 232,bypass duct 234, nozzle plug 238, turbine 240, shaft 242, turbineexhaust case 244, and strut 246. Furthermore, gas turbine engine 210includes inner seal 248 and outer seal 250.

Core 224 is circumscribed by aft nacelle 232, which is slidable in theaft direction. Bypass duct 234 is a plenum through which a bypassairstream can flow. Nozzle plug 238 is arranged aft of turbine 240.Turbine 240 rotates about shaft 242, and turbine exhaust case 244provides egress for exhaust gases from turbine 240. Strut 246 passesthrough turbine exhaust case 244.

Aft nacelle 232 is slidable in the fore and aft directions. Core 224engages with nozzle plug 238. Core 224 includes turbine section 240 andshaft 242. Core 224 can exhaust air radially outward of nozzle plug 238from centerline C_(L) through turbine exhaust case (TEC) 244.

TEC 244 is a passage from turbine section 240 in the aft direction,supported by struts 246. Bypass air is routed through bypass duct 234,which is located radially further outward from turbine exhaust case 244.

Nozzle plug 238 engages with core 224 at inner seal 248 Likewise, TEC244, which is fixed to core 224, engages with the slidable portion 214at outer seal 250. As shown in FIG. 5A, inner seal 248 and outer seal250 are both W-shaped seals. Thus, an airstream passing through turbine240 is not able to pass through inner seal 248 to nozzle plug 238 orturbine exhaust case 244. Likewise, an airstream is not able to escapeTEC 244 through either of inner seal 248 nor outer seal 250.

Core 224 is often left in place while slidable portion 214 is moved inthe aft direction, as previously described with respect to earlierfigures, in order to facilitate maintenance, inspection, or repair ofgas turbine engine 210. Nozzle plug 238 is shaped to accomplish variousobjectives, such as to maximize efficiency of gas turbine engine 210 orreduce exhaust noise during engine operation. Often, as shown in FIG.5A, nozzle plug 238 must be movable with slidable portion 214 or else itwill impinge movement of slidable portion 214 in the aft direction.

Inner seal 248 and outer seal 250 enable nozzle plug 238 to be sealed tocore 224 during operation, but removed during partially open or openconditions (i.e., when slidable portion 214 is moved in the aftdirection from the position shown in FIG. 4A).

In FIG. 5B, gas turbine engine 210 is in a partially open condition.Nozzle plug 238 is a part of slidable portion 214, and thus nozzle plug238 is axially spaced aft from core 224. This arrangement illustratesthe functions of inner seal 248 and outer seal 250 of FIG. 5A.

Inner seal 248 includes inner seal outer portion 248A on nozzle plug 238and inner seal inner portion 248B on TEC 244. When gas turbine engine210 is in the closed position, as previously described with respect toFIG. 5A, inner seal outer portion 248A and inner seal inner portion 248Bengage to prevent ingress or egress of air at inner seal 248. Likewise,outer seal outer portion 250A on TEC 244 and outer seal inner portion250B on slidable portion 214 engage to prevent ingress or egress of airat outer seal 250 of FIG. 5A.

During repair, maintenance, and/or inspection, it is not necessary tomaintain an airtight seal between inner seal outer portion 248A andinner seal inner portion 248B, nor between outer seal outer portion 250Aand outer seal inner portion 250B. Furthermore, in some embodimentsseparation of nozzle plug 238 from core 224 with slidable portion 214 isbeneficial. The structures described above provide for a movable nozzleplug that nonetheless prevents air leakage between the plena separatedby inner seal 248 and the plena separated by outer seal 250.

Discussion of Possible Embodiments

The following are non-exclusive descriptions of possible embodiments ofthe present invention.

A gas turbine engine nacelle includes a first annular portion that isstationary and adapted for partially surrounding an engine core. Thefirst annular portion includes a fore pylon connecting portion. A railis coupled to the fore pylon connecting portion and extending in the aftdirection from the first annular portion. A second annular portion, aftof the first annular portion and coupled to the rail, is movable alongan engine core centerline between a closed position and at least oneopen position. The second annular portion is configured to engage withthe first annular portion when the second annular portion is in theclosed position, thereby providing access to the engine core. A guidepin extends forward from the second annular portion. A locking mechanismis disposed within the first annular portion for engaging the guide pinwhen the second annular portion is in the closed position.

The gas turbine engine nacelle of the preceding paragraph can optionallyinclude, additionally and/or alternatively, any one or more of thefollowing features, configurations and/or additional components:

According to another embodiment, a sliding nacelle includes an annularportion coupled to a rail and movable along the rail between a closedposition and at least one open position. The annular portion isconfigured to engage with a fore nacelle having a locking mechanism whenthe annular portion is in the closed position. A guide pin extendsforward from the annular portion.

The sliding nacelle of the preceding paragraph can optionally include,additionally and/or alternatively, any one or more of the followingfeatures, configurations, steps, and/or additional components:

The guide pin may include a pin shaft with an expansive tip at its freeend.

The expansive tip may be a spearhead comprising a front segment taperedto point toward the fore nacelle, and a back segment tapered to pointtoward the annular portion.

The front segment and the back segment may be conically shaped.

The locking mechanism may include a cavity configured to receive theguide pin, and a plurality of collars configured to engage the guidepin.

The collars may be configured to substantially match the profile of theback segment.

The sliding nacelle may further comprise a plurality of guide pins eachconfigured to engage a locking mechanism of the fore nacelle in theclosed position.

While the invention has been described with reference to an exemplaryembodiment(s), it will be understood by those skilled in the art thatvarious changes may be made and equivalents may be substituted forelements thereof without departing from the scope of the invention. Inaddition, many modifications may be made to adapt a particular situationor material to the teachings of the invention without departing from theessential scope thereof. Therefore, it is intended that the inventionnot be limited to the particular embodiment(s) disclosed, but that theinvention will include all embodiments falling within the scope of theappended claims.

1. A gas turbine engine nacelle comprising: a first annular portion thatis stationary and adapted for partially surrounding an engine core, thefirst annular portion including a fore pylon connecting portion; a railcoupled to the fore pylon connecting portion and extending in the aftdirection from the first annular portion; a second annular portion, aftof the first annular portion and coupled to the rail, the second annularportion movable along an engine core centerline between a closedposition and at least one open position, wherein the second annularportion is configured to engage with the first annular portion when thesecond annular portion is in the closed position, thereby providingaccess to the engine core; a guide pin extending forward from the secondannular portion; and a locking mechanism, disposed within the firstannular portion, for engaging the guide pin when the second annularportion is in the closed position.
 2. The gas turbine engine nacelle ofclaim 1, wherein the guide pin comprises a pin shaft with an expansivetip at its free end.
 3. The gas turbine engine nacelle of claim 2,wherein the expansive tip forms a spearhead shape.
 4. The gas turbineengine nacelle of claim 3, wherein the spearhead comprises: a frontsegment tapered to point toward the first annular portion; and a backsegment tapered to point toward the second annular portion.
 5. The gasturbine engine nacelle of claim 4, wherein the front segment and theback segment are conically shaped.
 6. The gas turbine engine nacelle ofclaim 1, wherein the locking mechanism comprises: a cavity configured toreceive the guide pin; and a plurality of collars configured to engagethe guide pin.
 7. The gas turbine engine nacelle of claim 6, wherein thecollars are configured to substantially match the profile of the backsegment.
 8. The gas turbine engine nacelle of claim 1, and furthercomprising a plurality of locking mechanisms configured to engage aplurality of guide pins when the gas turbine engine is in the closedposition.
 9. A sliding nacelle for a gas turbine engine comprising: anannular portion coupled to a rail and movable along the rail between aclosed position and at least one open position, wherein the annularportion is configured to engage with a fore nacelle having a lockingmechanism when the annular portion is in the closed position; and aguide pin extending forward from the annular portion.
 10. The slidingnacelle of claim 9, wherein the guide pin comprises a pin shaft with anexpansive tip at its free end.
 11. The sliding nacelle of claim 10,wherein the expansive tip is a spearhead comprising: a front segmenttapered to point toward the fore nacelle; and a back segment tapered topoint toward the annular portion.
 12. The sliding nacelle of claim 11,wherein the front segment and the back segment are conically shaped. 13.The sliding nacelle of claim 11, wherein the locking mechanismcomprises: a cavity configured to receive the guide pin; and a pluralityof collars configured to engage the guide pin.
 14. The sliding nacelleof claim 13, wherein the collars are configured to substantially matchthe profile of the back segment.
 15. The sliding nacelle of claim 9, andfurther comprising a plurality of guide pins each configured to engage alocking mechanism of the fore nacelle in the closed position.